P-51D TIP (BL215) AIRFOIL (p51dtip-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: P-51D TIP (BL215) AIRFOIL (p51dtip-il) Reynolds number: 50,000 Max Cl/Cd: 23.23 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-p51dtip-il-50000-n5.txt Download as CSV file: xf-p51dtip-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: P-51D TIP (BL215) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5047 0.10399 0.09756 -0.0341 1.0000 0.0505
-10.250 -0.5056 0.09899 0.09264 -0.0373 1.0000 0.0503
-10.000 -0.5078 0.09365 0.08735 -0.0409 1.0000 0.0498
-9.750 -0.5127 0.08794 0.08171 -0.0453 1.0000 0.0495
-9.500 -0.5208 0.08261 0.07643 -0.0492 1.0000 0.0488
-9.250 -0.5323 0.07794 0.07178 -0.0521 1.0000 0.0480
-9.000 -0.5486 0.07421 0.06806 -0.0532 1.0000 0.0478
-8.750 -0.5692 0.07168 0.06554 -0.0515 1.0000 0.0468
-8.500 -0.5890 0.06954 0.06335 -0.0489 0.9943 0.0464
-8.250 -0.5885 0.06498 0.05850 -0.0513 0.9806 0.0468
-8.000 -0.5830 0.06049 0.05366 -0.0533 0.9714 0.0474
-7.750 -0.5768 0.05629 0.04906 -0.0542 0.9627 0.0478
-7.500 -0.5648 0.05201 0.04426 -0.0551 0.9564 0.0480
-7.250 -0.5536 0.04842 0.04018 -0.0548 0.9493 0.0487
-7.000 -0.5358 0.04480 0.03596 -0.0550 0.9443 0.0500
-6.750 -0.5210 0.04214 0.03260 -0.0541 0.9386 0.0543
-6.500 -0.5004 0.04006 0.03043 -0.0543 0.9344 0.0596
-6.250 -0.4746 0.03735 0.02716 -0.0543 0.9310 0.0617
-6.000 -0.4485 0.03506 0.02433 -0.0540 0.9274 0.0639
-5.750 -0.4214 0.03310 0.02201 -0.0536 0.9238 0.0667
-5.500 -0.3909 0.03151 0.02031 -0.0539 0.9210 0.0712
-5.250 -0.3605 0.03042 0.01896 -0.0545 0.9184 0.0818
-5.000 -0.3269 0.02939 0.01772 -0.0550 0.9165 0.0886
-4.750 -0.3035 0.02861 0.01677 -0.0539 0.9135 0.0927
-4.500 -0.2861 0.02792 0.01603 -0.0524 0.9098 0.0980
-4.250 -0.2671 0.02728 0.01526 -0.0512 0.9064 0.1057
-4.000 -0.2479 0.02650 0.01451 -0.0503 0.9033 0.1199
-3.750 -0.2354 0.02563 0.01390 -0.0484 0.8997 0.1533
-3.500 -0.2380 0.02394 0.01336 -0.0448 0.8951 0.3322
-3.250 -0.2398 0.02454 0.01532 -0.0359 0.8921 0.7080
-3.000 -0.1523 0.02800 0.01852 -0.0332 0.8969 0.8845
-2.750 -0.1081 0.02795 0.01810 -0.0363 0.8960 0.8998
-2.500 -0.0670 0.02780 0.01762 -0.0395 0.8946 0.9081
-2.250 -0.0473 0.02777 0.01740 -0.0388 0.8918 0.9154
-2.000 -0.0152 0.02765 0.01707 -0.0406 0.8898 0.9187
-1.750 0.0106 0.02758 0.01681 -0.0413 0.8876 0.9213
-1.500 0.0182 0.02769 0.01684 -0.0387 0.8838 0.9255
-1.250 0.0277 0.02779 0.01685 -0.0365 0.8808 0.9295
-1.000 0.0500 0.02784 0.01680 -0.0366 0.8786 0.9318
-0.750 0.0738 0.02790 0.01676 -0.0369 0.8764 0.9344
-0.500 0.0975 0.02799 0.01677 -0.0372 0.8744 0.9372
-0.250 0.1066 0.02818 0.01692 -0.0349 0.8714 0.9411
0.000 0.1210 0.02837 0.01708 -0.0337 0.8690 0.9447
0.250 0.1420 0.02856 0.01726 -0.0337 0.8669 0.9480
0.500 0.1623 0.02876 0.01745 -0.0335 0.8646 0.9515
0.750 0.1822 0.02898 0.01767 -0.0332 0.8624 0.9550
1.000 0.2064 0.02923 0.01794 -0.0337 0.8609 0.9582
1.250 0.2343 0.02952 0.01828 -0.0349 0.8597 0.9613
1.500 0.2463 0.02986 0.01866 -0.0335 0.8568 0.9672
1.750 0.2634 0.03018 0.01905 -0.0329 0.8540 0.9724
2.000 0.2858 0.03055 0.01950 -0.0334 0.8521 0.9771
2.250 0.3091 0.03093 0.02001 -0.0339 0.8500 0.9827
2.500 0.3371 0.03135 0.02055 -0.0353 0.8480 0.9881
2.750 0.3648 0.03181 0.02115 -0.0366 0.8464 0.9947
3.000 0.3638 0.03220 0.02163 -0.0330 0.8422 1.0000
3.250 0.3616 0.03250 0.02199 -0.0289 0.8373 1.0000
3.500 0.3856 0.03289 0.02252 -0.0289 0.8324 1.0000
3.750 0.3883 0.03310 0.02285 -0.0253 0.8226 1.0000
4.000 0.4091 0.03340 0.02330 -0.0246 0.8130 1.0000
4.250 0.4403 0.03379 0.02391 -0.0255 0.8056 1.0000
4.500 0.4575 0.03412 0.02442 -0.0242 0.7948 1.0000
4.750 0.5000 0.03401 0.02470 -0.0258 0.7788 1.0000
5.000 0.5347 0.03353 0.02454 -0.0256 0.7570 1.0000
5.250 0.5811 0.03210 0.02354 -0.0255 0.7283 1.0000
5.500 0.6216 0.02820 0.01999 -0.0208 0.6649 1.0000
5.750 0.6122 0.02823 0.02012 -0.0155 0.6176 1.0000
6.000 0.5969 0.02937 0.02134 -0.0112 0.5587 1.0000
6.250 0.6357 0.02736 0.01694 -0.0047 0.1838 1.0000
6.500 0.6396 0.02913 0.01824 -0.0023 0.1349 1.0000
6.750 0.6507 0.03066 0.01955 -0.0005 0.1118 1.0000
7.000 0.6683 0.03204 0.02086 0.0009 0.0967 1.0000
7.250 0.6903 0.03324 0.02209 0.0017 0.0790 1.0000
7.500 0.7367 0.03483 0.02383 0.0010 0.0665 1.0000
7.750 0.7815 0.03676 0.02593 -0.0006 0.0539 1.0000
8.000 0.8208 0.03956 0.02883 -0.0018 0.0475 1.0000
8.250 0.8532 0.04276 0.03256 -0.0019 0.0443 1.0000
8.500 0.8737 0.04534 0.03537 -0.0015 0.0406 1.0000
8.750 0.8889 0.04841 0.03874 -0.0006 0.0378 1.0000
9.000 0.8989 0.05178 0.04267 0.0010 0.0360 1.0000
9.250 0.9053 0.05540 0.04673 0.0027 0.0353 1.0000
9.500 0.9065 0.05909 0.05082 0.0045 0.0350 1.0000
9.750 0.9028 0.06276 0.05484 0.0064 0.0348 1.0000
10.000 0.8939 0.06632 0.05868 0.0084 0.0347 1.0000
10.250 0.8809 0.06993 0.06254 0.0103 0.0348 1.0000
10.500 0.8653 0.07386 0.06667 0.0113 0.0349 1.0000
10.750 0.8485 0.07808 0.07108 0.0115 0.0352 1.0000
11.000 0.8293 0.08289 0.07604 0.0107 0.0354 1.0000
11.250 0.8103 0.08821 0.08148 0.0090 0.0358 1.0000
11.500 0.7910 0.09432 0.08769 0.0062 0.0362 1.0000
11.750 0.7741 0.10099 0.09441 0.0025 0.0366 1.0000
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Polar data table (+)
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